Thrust reverser system exhibiting limited aerodynamic perturbation

Abstract

A thrust reverser system includes a thrust reversal cascade and a reverser door which are accommodated in a housing situated outside a secondary flow duct. The system also includes connection parts the presence of which combined with the action of the actuator gives rise simultaneously to: displacement rearwards of the cascade in the direction of a nacelle opening, cleared by a nacelle cowling entrained rearwards together with the cascade; and a combined movement of the reverser door relative to the cascade, leading to displacement of the front end of the door rearwards along the cascade, and to pivoting of this door, such as to give rise to plunging of its rear end into the secondary flow duct.

The invention claimed is: 
     
       1. A thrust reverser system for a turbine engine of a double-spool aircraft, the reverser system comprising:
 at least one thrust reversal cascade through which the air of a secondary flow duct of the turbine engine is configured to circulate in the active configuration of the reverser system; 
 at least one reverser door configured to close the secondary flow duct at least partly when the reverser system is in the active configuration; 
 at least one actuator, 
 wherein, in an inactive configuration of the reverser system, the at least one reverser door is accommodated in a housing situated outside the secondary flow duct, and in which housing there is also located the at least one thrust reverser cascade entrained by the at least one actuator, and a rear end of which cascade is integral with a nacelle outer mobile cowling, the reverser system also comprising: 
 a first connection part, a first end of which is connected inside the nacelle outer mobile cowling by a first articulated connection, and a second end of which is connected to the at least one reverser door by a second articulated connection; 
 a second connection part, a first end of which is connected to a rear end of the at least one reverser door by a third articulated connection, and a second end of which is connected to an inner wall of the secondary flow duct by a fourth articulated connection; 
 and wherein the at least one reverser door is fitted at a front end thereof on the cascade by a fifth connection which allows the front end to slide along the at least one thrust reverser cascade and to pivot relative to the at least one thrust reverser, the second articulated connection being arranged between the third articulated connection and the fifth connection, such that, during transition from the inactive configuration to the active configuration, the presence of the first and second connection parts combined with the action of the at least one actuator gives rise simultaneously to: 
 displacement rearwards of the at least one thrust reverser cascade in the direction of a nacelle opening, cleared by the nacelle outer mobile cowling entrained rearwards together with the cascade; and 
 a combined movement of the at least one reverser door relative to the at least one thrust reverser cascade, leading firstly to displacement of a front end of the at least one reverser door rearwards along the at least one thrust reverser cascade, and secondly to pivoting of the at least one reverser door according to the fifth connection, such as to cause plunging of the rear end into the secondary flow duct. 
 
     
     
       2. The reverser system according to  claim 1 , wherein, in the inactive configuration, the first connection part is accommodated in the housing, and the second connection part is accommodated partly in the housing. 
     
     
       3. The reverser system according to  claim 1 , wherein, in the inactive configuration, part of the second connection part is arranged substantially radially in the secondary flow duct, and is configured to be shielded from a secondary flow of air by an arm of an intermediate casing of the turbine engine, and
 in the active configuration, the second connection part is arranged locally substantially parallel to the inner wall of the secondary flow duct. 
 
     
     
       4. The reverser system according to  claim 1 , wherein the first connection part adopts a form globally of an “L”. 
     
     
       5. The reverser system according to  claim 1 , wherein the at least one actuator comprises an actuator rod articulated on a front end of the at least one thrust reverser cascade. 
     
     
       6. The reverser system according to  claim 1 , wherein the fifth connection comprises:
 at least one door guide rail integral with the at least one thrust reverser cascade, and extending along the at least one thrust reverser; and 
 a roller which cooperates with the at least one guide rail, and is fitted on the front end of the at least one reverser door. 
 
     
     
       7. The reverser system according to  claim 1 , wherein the housing is an inner space of the nacelle. 
     
     
       8. The reverser system according to  claim 1 , wherein, in the inactive configuration, the at least one thrust cascade and the at least one reverser door are substantially parallel, and are each situated at least partly radially opposite a fan casing of the turbine engine. 
     
     
       9. The reverser system according to  claim 1 , the at least one thrust reverser cascade comprises a plurality of thrust reverser cascades adjacent in the tangential direction of the turbine engine, such as to form an assembly of cascades extending over an angular sector of 300 to 360° around a longitudinal axis of the turbine engine, and wherein each cascade is associated with a reverser door. 
     
     
       10. The reverser system according to  claim 9 , wherein the cascades are connected to one another mechanically, such that the number of actuators is smaller than the number of cascades. 
     
     
       11. A double-spool aircraft turbine engine comprising a thrust reverser system according to  claim 1 . 
     
     
       12. An aircraft comprising at least one turbine engine according to  claim 11 .